2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)最新文献

{"title":"Co-design of an Integrated Direct-drive Electric Motor and Ducted Propeller for Aircraft Propulsion","authors":"T. Balachandran, John David Reband, Jianqiao Xiao, Samith Sirimmana, Ranbir Dhilon, K. Haran","doi":"10.2514/6.2020-3560","DOIUrl":"https://doi.org/10.2514/6.2020-3560","url":null,"abstract":"This paper discusses the co-design of an electric aircraft propulsion system for minimum weight and maximum power-to-thrust efficiency. The system under consideration for preliminary exploration of the methodology consists of a fully superconducting synchronous motor and a ducted, fixed-pitch propeller. In order to ensure a viable propulsor, a minimum required thrust bound is imposed on the system design. Both analytical methods and finite-element analysis (FEA) are used to size the motor, and a blade-element momentum (BEM) model is implemented for predicting performance of the ducted propeller. A genetic algorithm optimization scheme is applied on a hydrogen-powered electric aircraft propulsion system proposed for the Center for High-Efficiency Electrical Technologies for Aircraft (CHEETA) project. Sensitivity of the combined system efficiency to motor weight is evaluated.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"81 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126221089","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Design and evaluation of a high power density 5 MW, 6000 RPM fully- superconducting generator","authors":"J. Voccio, J. Tangudu","doi":"10.2514/6.2020-3551","DOIUrl":"https://doi.org/10.2514/6.2020-3551","url":null,"abstract":"In order to reduce carbon emissions, there is considerable interest in both superconducting generators and motors to enable all-electric aircraft for transportation. This paper summarizes the results of an initial design study for a 5 MW, 6000 rpm fully-superconducting generator. Using the FEMM magnetics code and the Lua scripting language, electromagnetic optimization was performed to determine the best cases. This study also considered ac loss capability of Bi-2212 superconductors, which can operate in the 30 to 40 K temperature range, along with the associated cryogenic refrigeration requirements. Initial results show that, while machines with active weight densities of ~40 kW/kg are possible, the weight of the associated cryocoolers would be prohibitive; however, the use of liquid hydrogen makes these machines realizable. Future cryocooler development is required to get their specific weights down to ~3 kg/kW of input power.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"38 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116502945","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Outer Stator Magnetically-Geared Motors for Electrified Urban Air Mobility Vehicles","authors":"Thomas F. Tallerico, Zachary A. Cameron, J. Scheidler, Hashmatullah Hasseeb","doi":"10.2514/6.2020-3563","DOIUrl":"https://doi.org/10.2514/6.2020-3563","url":null,"abstract":"Electrified urban air mobility vehicles require advances in the specific power, efficiency, and reliability of electric motor drivetrains. Gearing an electrified aircraft’s drivetrain generally leads to a lighter weight and/or more efficient drivetrain overall. Mechanical gears, however, due to their use of mechanical contact to transmit torque between gear bodies, have numerous wear and failure modes that lead to significant reliability and maintenance penalties. Magnetic gears, on the other hand, use magnetic fields instead of mechanical contact to transmit torque between gear bodies, and therefore have the potential to achieve the benefits of a geared drive system without reliability and maintenance penalties. Magnetic gears cannot match the specific torque of mechanical gears. Therefore simply trading a mechanical gear for a magnetic gear in a drive train will add mass. To make a magnetically-geared drive competitive with a mechanically geared drive in terms of mass, the magnetic gear and the electric motor in the drive train have to be integrated to share magnetic and mechanical components. One way of integrating a magnetic gear and a motor is called an outer stator magnetically-geared motor. In this paper, the outer stator magnetically-geared motor is assessed for its potential in urban air mobility vehicles. A design tool for outer stator magnetically-geared motors is developed. The tool is used to create a preliminary design of a 100 kW outer stator magnetically-geared motor. High fidelity analysis of that design is used to finalize it and update the design tool. Additional design tool results are produced to estimate the potential of the outer stator magnetically-geared motor for a 100 kW urban air mobility drive.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128284268","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Reducing Mission Cryogenic Load via HTS Dynamo","authors":"K. Hamilton, D. Carnegie, R. Badcock","doi":"10.2514/6.2020-3552","DOIUrl":"https://doi.org/10.2514/6.2020-3552","url":null,"abstract":"Electric motors based on conventional conductive materials such as copper and aluminium are limited in efficiency and power density by the resistive losses of these materials. Lighter and more efficient motors are possible when High Temperature Superconductor (HTS) materials are used as there are no resistive losses. Additionally, the high current density that may be supported by these materials enables alternative motor designs which leverage high magnetic fields to remove the requirement for iron components and reduce the overall motor volume. Despite HTS materials exhibiting superconductivity at much higher temperatures than other superconductive materials, cryogenic cooling to below 90 K is still required. Suitable cryocoolers typically have efficiencies below 20%. This unfavorably alters both the specific power and efficiency of HTS based motors when considering the motor as including all the associated hardware required for operation. Previously it has been shown that energizing the superconducting components of a motor wirelessly using a HTS dynamo can reduce the required mass of both the cryogenic refrigeration equipment, and the motor drive electronics. The work presented here investigates the reduction in total fuel burn of a 737 sized turboelectric aircraft that may be achieved when replacing a conventional DC power supply for the HTS motor field coils with a HTS Dynamo DC power supply.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116819120","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Select Variables Affecting Thermal System Design of a Liquid-Cooled Stator","authors":"A. Woodworth, Andrew D. Smith, R. Jansen, Gerald Szpak","doi":"10.2514/6.2020-3603","DOIUrl":"https://doi.org/10.2514/6.2020-3603","url":null,"abstract":"NASA Glenn Researchers have endeavored to create a high-power-density, efficient electric motor called the High Efficiency Megawatt Motor (HEMM) with a goal of exceeding 98% efficiency and 1.46 MW of power. These aggressive goals were set because increasing the power density and efficiency of electric machines (motors and generators) is integral to bringing electrified aircraft (EA) to commercial realization. Resistive losses in the stator windings are by far the largest (34%) contributor to this design’s total energy losses. Previous testing of a HEMM-like stator test article (statorette) showed good agreement between measured performance and model predictions. Therefore, a foundation was provided to test other engineering parameters that are encountered when designing an electric machine. Of particular interest are the effects of changes to the thickness of the epoxy from the potting process, changes in the fluid volume/flow path around the end windings, and changes in the viscosity of the cooling fluid on the overall thermal performance of the unit. The impact of those parameters as revealed through a third-generation build, test, and finite element model analysis of a statorette test section is the focus of this paper.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"65 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133480084","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Insulation Design and Optimization of Laminated Busbar for More Electric Aircraft Motor Drive under High Altitude and Depressurized Environments","authors":"Zhao Yuan, Yalin Wang, A. Emon, Zhongjing Wang, B. Narayanasamy, A. Deshpande, Hongwu Peng, F. Luo","doi":"10.2514/6.2020-3588","DOIUrl":"https://doi.org/10.2514/6.2020-3588","url":null,"abstract":"More electric aircrafts (MEA) recently attracts increasing attention due to improvements to efficiency, reduce weight, fuel cost, and carbon emissions. High-specific-power machines, and corresponding integrated motor drives have been identified as the crucial enabling technology for the realization of more electric aircraft propulsion. Such a concept requires converter working under depressurized environments, which poses challenges to the electric insulation due to partial discharge (PD). This threatens the reliability of the drive system. This paper proposes an insulation design and optimization methodology for a laminated busbar in a 450-kVA electric-aircraft motor drive. The design aims to avoid any partial discharge in the insulation and also achieves optimized busbar stray inductance. To achieve the targets, partial discharge inception voltage (PDIV) with respect to air pressure was obtained by the experiment, and the experimental results were used as PD -free design criteria in electric field simulation of the laminated busbar. Then, the insulation structure regarding insulation material selection and thickness selection was optimized by taking both the PD-free criteria and parasitic inductance into consideration. The proposed design procedure provides valuable references for future laminated busbar design, which is used for the MEA system.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124554117","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Mathematical Correlations, Method for the Preliminary Sizing, Design and Tests of an Ultralight All-Electric Aircraft","authors":"J. A. Posada-Montoya, Fabián Vargas-Álvarez","doi":"10.2514/6.2020-3582.vid","DOIUrl":"https://doi.org/10.2514/6.2020-3582.vid","url":null,"abstract":"Aviation has a great impact on climate change, resource depletion, and human health. Sixty billion gallons of jet fuel are annually consumed worldwide, and more than 781 tons of CO2 were emitted in 2015. Tetraehtyl lead remains an additive to general aviation fuel; which causes neurotoxic effects, pollution, encephalopathy, low intellectual capacity, and renal tubular damage. 16 million of Americans live and 3 million of children study close to a general aviation airport. Although there have been improvements in fossil fuel motors efficiency, CO2 emissions, and biofuels; all-electric aircraft exceeds those improvements. The advantages of all-electric aircraft are lower noise, pollution, vibration, maintenance, and energy cost; instantaneous and reliable startup; no altitude effects; torque-speed characteristics; and distributed propulsion. Their main disadvantages are its cost, availability, maturity, low range, and endurance (due to the low specific energy of the batteries). Norway plans all short-haul flights (15-30 min) to be on electric 25-to-30 seat aircraft by 2040. The Swedish flight-shaming movement is causing passengers to move by train. Although several all-electric aircraft prototypes have been built and tested, there are no mathematical correlations and equations that allow the designer to estimate the motor power, and take-off, battery, and motor weight. Mathematical correlations and equations were elaborated based on the data obtained from the manufacturers of 34 all-electric aircraft. This paper presents the continuous power, weight, and power density of 19 electric aircraft motors that have been used in all-electric aircraft, and are available for new designs. The Predator 50-6 Evo electric motor produces 19 kW of continuous power and has a specific power of 8.3 kW.kg-1, while Siemens SP260D produces 261 kW and has a specific power of 5.2 kW.kg-1; and the Magnix Magni500 produces 560 kW and has a specific power of 4.1 kW.kg-1. Similarly, the voltage, capacity, energy, weight, and specific energy of five high specific energy lithium batteries are presented. LiNiMnCo and LiS batteries have obtained specific energies of 260 Wh.kg-1. Additionally, a preliminary approach was defined to estimate the weight and power of all-electric aircraft during cruise, take-off, and climb. Based on Michael Sandlin’s Goat 4 and Dale Kramer’s electric Lazair, a single-seat ultralight-glider all-electric aircraft was designed and built with a tricycle fixed landing gear. 6061T6 aluminum tube, aviation hardware, and uncertified Dacron 2.97 oz.yd-2 fabric was used to build the structure. The wing span is 36 ft, the wing area is 174 ft2, and the empty weight is 109 kg. 626 INR-18650-35E Samsung 3500 mAh lithium ion cells were spot welded in series and parallel to form two battery packs of 14S, 58.8 V, 78.2 Ah, and 4.5 kWh each. These packs are protected by two 300 A 14S Li-ion bluetooth MOS-screen Battery Management System (BMS). Two Turnigy Dlux 250A HV 6","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121021791","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Parallel Hybrid Propulsion & Secondary Power System Architecture Exploration and Evaluation","authors":"C. Lents, Zubair A. Baig, Russell D. Taylor","doi":"10.2514/6.2020-3555","DOIUrl":"https://doi.org/10.2514/6.2020-3555","url":null,"abstract":"The parallel hybrid turbofan propulsion (PHTF) system, with a high and low spool connected motor/generator, applied to a single aisle aircraft, has been study extensively and been shown to provide both gas turbine level and aircraft level benefits. With significant electrification of the propulsion system, the degree of subsystem electrification should also be considered. Thus this current study focuses on the PHTF, considering not only the PHTF operating modes but also the secondary power subsystems (electric, hydraulic, and pneumatic) which interface with the propulsion system. Secondary power subsystem options range from hydraulic or electric for actuation to pneumatic or electric for the environmental control system. Each combination has been explored and evaluated within the UTRC aircraft systems integrated model (ASIM) – architecture exploration and evaluation (AEE) framework to identify the aircraft subsystem architecture that best complements the preferred hybrid propulsion system, where the hybrid propulsion system encompasses low and high spool machine size, usage scenario, and boost power source. Energy cost reduction and technology risk are evaluated for each design space architecture. The results show that a mild PHTF, using a low level of stored electric energy is preferred with a combination of electric and hydraulic actuation, electric wing anti-ice, and electric engine accessories. A bleed and electric based pneumatic system, each pared with an ECS optimized for the type of pneumatic system show similar energy cost performance.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123861787","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Conceptual Design and Operating Costs Evaluation of a 19-seat All-Electric Aircraft for Regional Aviation","authors":"Matheus Medeiros Maciel Monjon, Cesar Monzu Freire","doi":"10.2514/6.2020-3591.c1","DOIUrl":"https://doi.org/10.2514/6.2020-3591.c1","url":null,"abstract":"This paper presents a conceptual approach for the design of an all-electric short-range aircraft for regional aviation. By using the designed aircraft and based on market and financial assumptions, the operating costs were calculated, and by means of trade analysis, an investigation of the influence of few parameters was performed. As a result, the designed aircraft reached an estimated reduction of 39% in the Direct Operating Costs (DOC) considering a frequency of 4 daily flights. Reductions in fuel costs also reached up to 80% in comparison to the current turboprop segment. Moreover, the findings indicate that the maintenance and depreciation take most of the DOC cost for most of the daily flight frequency, with the battery replacement cost increasing significantly with the increase in the daily number of flights. By a sensibility analysis was also identified that variations in the battery life cycle and aircraft purchase price cause more significant changes in the DOC than other parameters considered that could carry uncertainties.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121972414","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Anatomy of a 20 MW Electrified Aircraft: Metrics and Technology Drivers","authors":"P. Kshirsagar, J. Ewanchuk, B. V. van Hassel, Russell D. Taylor, S. Dwari, J. Rheaume, C. Lents","doi":"10.2514/6.2020-3581","DOIUrl":"https://doi.org/10.2514/6.2020-3581","url":null,"abstract":"Development of electric, hybrid and turboelectric propulsion technologies for electrified aircraft propulsion system is essential for improving fuel consumption, reducing emissions and noise pollution, lowering maintenance costs and improving reliability of the air transportation systems. The future needs and key benefits of aircraft electrification has made it a highly persuaded common technology trend across the aerospace industry ranging from very large airplanes to small aircrafts, all alike. For very high power (20MW) propulsion system, with the inadequacies of current and near future state-of-the art of electric energy storage technologies, all electric aircraft solution faces enormous technology gaps that needs to be bridged. Advanced turbo-electric technology offers potential solutions towards successful realization of the benefits of electrification of aircrafts. However, this represent a grand challenge in many fronts to realize electric drivetrain (EDT) designs that would significantly improve fuel burn reduction, design flexibility, and operational improvements in next generation of aircrafts. This work focuses on the underlying technological elements to enable such high power turbo-electric aircraft. A preliminary study is carried out to find that to achieve the key benefits of electrifications, the ETD system efficiency has to be > 93% and the specific power density of the system is required to be > 7.5 kW/kg. Furthermore, it is found that that to achieve such system level performances, the EDT components is required to be ≥ 99% and with specific power densities > 40 kW/kg to achieve the 7.5 kW/kg target. These necessitates orders of magnitude of improvements at all technological fronts and requires radical improvement in design and integration methodologies. Major technologies and design trades for various components and system architectures are presented to provide guidelines and framework to address this grand challenge. Key results are provided to support the design study.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116986861","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}